AN EXTRACTION OF THE DOMINANT ROTOR-STATOR INTERACTION MODES BY THE USE OF POD TECHNIQUE IN A LOW PRESSURE CENTRIFUGAL COMPRESSOR

Size: px
Start display at page:

Download "AN EXTRACTION OF THE DOMINANT ROTOR-STATOR INTERACTION MODES BY THE USE OF POD TECHNIQUE IN A LOW PRESSURE CENTRIFUGAL COMPRESSOR"

Transcription

1 U.P.B. Sci. Bull., Series D, Vol. 73, Iss. 1, 2011 ISSN AN EXTRACTION OF THE DOMINANT ROTOR-STATOR INTERACTION MODES BY THE USE OF POD TECHNIQUE IN A LOW PRESSURE CENTRIFUGAL COMPRESSOR Mihai NICULESCU 1, Sterian DĂNĂILĂ 2 Metoda descompunerii în moduri proprii ortogonale (POD) este folosită pentru analiza câmpurilor de viteză si de presiune dintr-un compresor centrifugal cu grad de comprimare mic, obţinute prin simulări numerice. În comparaţie cu orice altă descompunere, metoda descompunerii în moduri proprii ortogonale ne furnizează cea mai bună aproximatie modală pentru orice număr luat de moduri proprii. Modurile proprii ortogonale arată caracteristicile interacţiunii nestaţionare rotor-stator precum şi erorile numerice. The Proper Orthogonal Decomposition (POD) method is applied to the velocity and pressure fields from a low-pressure centrifugal compressor. The processed data come from numerical simulations. In comparison with any other decomposition, the POD gives the best modal approximation in terms of the energy expressed on any given number of modes to be taken into account. The POD modes show the behavior of unsteady rotor-stator interaction as well as the numerical errors. Keywords: unsteady rotor-stator interaction, proper orthogonal decomposition, CFD. 1. Introduction The flow in turbomachinery is complex: three-dimensional, viscous, and unsteady, with time scales that vary considerably. This behavior makes difficult the complete flow analysis. Usually, in the industrial practice, the flow is assumed steady in the reference frame linked to the studied row. Furthermore, one can consider that every flow is composed by a main flow and a secondary flow that contains physical phenomena with no null velocity rotor. The secondary flows are characterized by vorteces that lead to three-dimensional behavior of flow and generate the losses due to the entropy increase. There are some sources of unsteady phenomena, in turbomachinery and they are described after their origin [1]. Because the unsteady rotor-stator interaction can affect dramatically the turbomachinery performance, we paid it a 1 Ph. D. Student., Aerospace Engineering Faculty, University POLITEHNICA of Bucharest, Romania, mihai.niculescu@comoti.ro 2 Professor, Aerospace Engineering Faculty, University POLITEHNICA of Bucharest, Romania

2 140 Mihai Niculescu, Sterian Dănăilă special attention in this paper. The majority of researchers that studied this interaction from the numerical point of view focused their research on transonic turbomachinery; therefore, there is very few information about the unsteady rotorstator interaction for low velocity turbomachinery. Moreover, a recent study showed important discrepancies between experimental and numerical results for a low-pressure centrifugal stage [2]. Unfortunately, this study did not succeed to identify the effects that caused the major discrepancies between experimental and numerical results. For this reason, we have considered that it is useful to study the rotor-stator interactions in a low-pressure centrifugal stage. Up to now, the Fourier transform is a common tool for data storage or for the analysis of any periodic signal. Some recent studies [3, 4] clearly showed that POD is a more efficient method to extract the dominant modes involved in unsteady flow field. Unfortunately, these studies applied POD only for onedimensional decompositions. In order to take the full advantage of POD method, we have applied it for decomposition of full three-dimensional flow field. 2. Nomenclature e internal energy (J/kg); f external acceleration (m/s 2 ) h static enthalpy (J/kg) I rothalpy (m 2 /s 2 ) p static pressure (Pa); q v heat source (W/m 3 ) R gas constant (J/(kg K)); T static temperature (K); t time (s) u i Cartesian components of velocity (m/s) v i Cartesian components of absolute velocity (m/s) w i Cartesian components of relative velocity (m/s) x i Cartesian components of position vector (m) δ ij Kronecker delta; κ thermal conductivity (W/(m K)) μ dynamic viscosity (kg/(m s)); μ t eddy viscosity (kg/(m s)) ρ static density (kg/m 3 ); τ shear stress tensor (Pa) ε Levi-Civita symbol; ijk Ω i Cartesian components of angular velocity (rad/s) Subscript t turbulent; Superscript eff effective (laminar + turbulent)

3 An extraction of the dominant rotor-stator interaction modes by the use of POD technique Governing equations For a three-dimensional rotating Cartesian coordinate system, the unsteady Reynolds-averaged Navier-Stokes equations using the Favre averaging (a massweighted averaging) could be written in the conservative form as [5, 6] ρ + ( ρui ) = 0 (1) t xi eff ( ρui) + ( ρuu i j) = ρ fi + ( τ pδ ) ij ij (2) t x x j eff T eff ( ρe) + ( ρuji) = ρ f juj + qv + κ + τij ui (3) t xj x j x j where energy E and rothalpy I are defined by: 2 2 w i v E = e + ri. (4) w i v I = h + ri (5) 2 2 wi = ui vri, vri = εijkω jxk (6) According to the Boussinesq hypothesis and Stokes postulates and hypothesis for a Newtonian fluid, the shear stresses τ eff may be written as eff u u i j 2 uk τ ij = ( μ+ μt ) + ( μ+ μt ) δij (7) xj x i 3 xk The Sutherland s formula could be used to determine the dynamic viscosity μ as a function of temperature, while the eddy viscosity μ t is computed with a turbulence model For gases, the gravitational acceleration is very small, therefore it can be neglected. Moreover, we can assume that the thermal conductivity is the single heat source; therefore the heat source q v is null: q v = 0 (8) The pressure is obtained from the equation of state of ideal gas p = ρrt (9) 4. Numerical simulation The numerical simulations of the three-dimensional viscous flow were carried out on a centrifugal compressor designed, manufactured and tested by COMOTI, with commercial CFD code FLUENT that is based on finite volume method where each unknown takes an average value on each discretization cell. The computational domain generated in Gambit was split into eight blocks to j

4 142 Mihai Niculescu, Sterian Dănăilă facilitate the building of a fully structured mesh as shown in Fig. 1. The mesh for which, the results are given, has about hexahedral cells for the impeller passage and hexahedral cells for the vaned diffuser passage. In order to decrease the computational time, impressively, the time discretization is made with a backward implicit first order scheme and multigrid technique is used. To take into account the physical properties of flow, the convective fluxes are discretized with Roe scheme, which is a Godunov-type scheme [5, 6]. Because the turbulence is not a critical issue of this study, we used the Spalart-Allmaras model, which is a one-equation model [7]. At the inlet, a uniform stagnation pressure ( Pa) and temperature (300 K) are imposed, turbulent viscosity ratio μ t /μ is 10 and the flow is normal to inlet. At the outlet, a uniform static pressure ( Pa) is imposed. At the left and right sides of computational domain, the rotational periodic boundary conditions are imposed. All the walls have been assumed adiabatic. The shaft speed of impeller is rpm. Fig. 1. Computational domain of centrifugal compressor 5. Proper orthogonal decomposition - POD In the field of fluid mechanics two approaches have been used for the POD. Historically the method of Continuous POD (or the classical method) of Lumley [8] is proceeded by the Snapshot POD of Sirovich [9]. More information regarding the application of the proper orthogonal decomposition in the analysis of turbulent flows together with a detailed bibliography is given in [10]. In this paper, we used the Snapshot POD because it is much more efficient from the numerical point of view. The POD is a method that reconstructs a data set from its projection onto an optimal base. Besides using an optimal base for data reconstruction the POD does not use any prior knowledge of the data set. That is why the basis is only data dependent and this is reason for which the POD is used also in analyzing the natural patterns of the flow field.

5 An extraction of the dominant rotor-stator interaction modes by the use of POD technique For the reconstruction of the dynamic behavior of a system, the POD decomposes the data set in two parts: a time dependent part, a k (t), that forms the orthonormal amplitude coefficients and a space dependent part, ψ k (x), that forms the orthonormal basis. The reconstructed data set is: M u( x, t) = ak ( t) ψ k ( x) (10) k = 1 where M is the number of time instant observations in the data set. We denote the error of the reconstructed data set as: m ε( x, t) = u( x, t) ak ( t) ψk ( x) (11) k = 1 The base from which the data set is reconstructed is said to be optimal in the sense that the average least squares truncation error is minimized for any given number ( m M ) of basis functions over all possible sets of orthogonal functions: ε m ( ε, ε) = (12) where the. is the ensemble average and (.,.) is the standard Euclidian inner product. It was shown that the minimization condition for the error ε(x,t) translates into maximum condition for: 2 u, ψ λ = (13) ( ψ, ψ ) This maximization can be proven to take place if the time independent base functions ψ(x) are obtained from the Fredholm integral equation: M Rij ( xx, ') ψ j ( x' ) dx' = λψi ( x) (14) j= 1 where R ij is the correlation kernel. In this way, we transform this into an eigenvalue problem and λ k is the eigenvalue corresponding of the eigenvector ψ k. Because we can consider the inner product as being the equivalent of an energy, the value of λ k is linked to the energy contained in mode ψ k and the involved optimization process can be summarized as follows: the data set is projected onto a basis that maximizes the energy content. In the classical approach of Lumley [8], the correlation matrix is constructed as a space correlation matrix. Solving the eigenvalue problem, we obtain directly the eigenvectors as the spatial modes and then use them in order to obtain the time-dependent coefficients a t = u x, t, ψ x (15) k ( ) ( ( ) k ( ))

6 144 Mihai Niculescu, Sterian Dănăilă In the Snapshot POD of Sirovich [9], the correlation matrix is a time correlation matrix: 1 C = u( x, t) u( x, t' ) dv V (16) V which is of the size of the square of the number of snapshots. From the time correlation matrix, we get the eigenvalues λ k and time dependent eigenvectors φ k (t). The spatial eigenmodes that are time independent, are computed according to the formula: 1 ψ k ( x) = φk () t u( x, t) dt μ (17) where k t μk = λk (18) For the reconstruction of u(x,t), we take into account only a small number of modes that contain the most energy: 6. Results m (, ) μφ ( ) ψ ( ) u x t = t x (19) k = 1 k k k The processed data are the absolute velocity magnitude and static pressure fields obtained from numerical simulations using the commercial CFD code Fluent. For each period, we took 20 snapshots and the time between adjacent snapshots is of Δt = μs; therefore, the Snapshot POD of Sirovich yields 20 eigenmodes for each considered field. Table 1 Fraction of total energy for the most energetic modes Mode Fraction of total energy for variation of static pressure field Fraction of total energy for variation of absolute velocity magnitude field E E E E E E E E E E E E E E E E E E E E-05

7 An extraction of the dominant rotor-stator interaction modes by the use of POD technique The very high efficiency of the proper orthogonal decomposition is clearly underlined by table 1. The sum of the first two modes represents 90.5% and 95.5% of the total energy, respectively for the variations of static pressure and absolute velocity magnitude fields while the sum of modes 6 to the last mode represents only 0.163% and 0.236% of the total energy, respectively for the variations of static pressure and absolute velocity magnitude fields. Therefore, both variations of static pressure and absolute velocity magnitude fields can be very accurately reconstructed using only the first five modes. Furthermore, these results confirm that the base from which the data set is reconstructed is indeed optimal. It the following, we give results for some control points placed in a section at mid height of blade of vaned diffuser, at the middle distance between the blade and the right periodic as shown in Fig. 2. The numbering of these control points is from upstream to downstream. Fig. 2. Placement of control points Fig. 3. The first four most energetic modes of variation of static pressure field The sum of the first three most energetic modes of variation of static pressure field is 97.1% of the total energy. These modes are physical because they show how the potential and wake effects affect the flow, especially in the impeller region. More exactly, the first mode that contains 64% of the total energy shows especially the potential effects that affect the flow in the impeller region. For this reason, the peak of this mode is located on the interface between impeller region and vaned diffuser region. The second mode contains 26.5% of the total energy

8 146 Mihai Niculescu, Sterian Dănăilă and it shows especially, the interaction between the wakes due to the blunt trailing edge of impeller blade and potential effects. The peak of this mode is also placed near the interface between impeller region and vaned diffuser region because, at the middle distance between rows, this interaction is usually maximal. The third mode has 6.6% of the total energy and it represents mainly, the potential effects and the interaction between the wakes due to the blunt trailing edge of impeller blade and potential effects that cannot be captured by the first two modes. The last modes contain only 2.9 of the total energy and represent mainly, the numerical errors that occur at the interface between rotating region and stationary region and due the rotational periodicity condition that is not too correct. Fortunately, they contain little energy. Fig. 4. The first four most energetic modes of variation of absolute velocity magnitude field The first two most energetic modes of variation of absolute velocity magnitude field contain as much as 95.5% of the total energy. The first mode has 54.9% of the total energy and it represents the interaction between wakes due to the blunt trailing edge of impeller blade and potential effects. According to theory of characteristics, this interaction affects especially the vaned diffuser region and its peak is located near the middle distance between impeller and vaned diffuser. The second mode contains 40.6% of total energy and it represents the interaction between wakes and potential effects in the vaned diffuser region as well as the propagation of potential effects in the impeller region. The third and fourth modes have 3.7% of the total energy and they contain both physical and numerical information. From the physical point of view, they contain the information regarding the interaction between potential effects as well as the influence of potential effects in the impeller region. From the numerical point of view, they represent the numerical errors that occur at the interface between rotating region and stationary region and due the rotational periodicity condition. Furthermore, one sees that the value of the third mode is not close to zero at the outlet boundary of computational domain because we imposed a uniform static pressure on this frontier and this is not too correct according to the theory of characteristics [5, 6]. Because the POD is a method that reconstructs a data set from its projection onto an optimal base, we need only four modes to rebuild the variations

9 An extraction of the dominant rotor-stator interaction modes by the use of POD technique of static pressure and absolute velocity fields accurately. We will rebuild them for two snapshots placed at half the period (the number of impeller blades is equal to the number of vaned diffuser blades) as shown in Figs. 5 and 6. Fig. 5. The first snapshot for which the reconstruction is built Fig. 6. The second snapshot for which the reconstruction is built Fig. 7. Reconstruction of absolute velocity magnitude field for snapshot 1

10 148 Mihai Niculescu, Sterian Dănăilă Fig. 8. Reconstruction of static pressure field for snapshot 1 Fig. 9. Reconstruction of absolute velocity magnitude field for snapshot 2 Fig. 10. Reconstruction of static pressure field for snapshot 2

11 An extraction of the dominant rotor-stator interaction modes by the use of POD technique Analyzing the Figs. 7-10, one observes that only four modes are enough to reconstruct accurately the variations of static pressure and absolute velocity magnitude fields. Furthermore, the points where the field u(x,t) has high absolute values are better reconstructed than the points with small absolute values because the data set is projected onto a basis that maximizes the energy content. In other words, points with high energy (information) are reconstructed more accurately than points with low energy. 7. Conclusions The POD method has been successfully applied to the decomposition and reconstruction of variations of fully three-dimensional static pressure and absolute velocity magnitude fields obtained from numerical simulations using the commercial CFD code Fluent. Both variations of static pressure and absolute velocity magnitude fields can be accurately reconstructed using only the first four modes; therefore, the proper orthogonal decomposition method is a very efficient method for the data storage of unsteady flows. Moreover, the POD technique is able to capture the relevant features of the unsteady rotor-stator interaction, especially, the potential effects and the interaction between wakes and potential effects. Furthermore, the POD method clearly shows the numerical errors such as those errors that occur at the interface between rotating region and stationary region because the information exchange does not use the characteristic variables, the reflection of numerical waves at rotational periodic and outlet boundaries as well as their magnitude. In order to obtain more accurate results [3, 11], we should impose the phase-lagged condition, which is not yet available in Fluent, on the left and right sides of computational sides, instead of the rotational periodicity condition. Acknowledgments The present work has been supported from the National University Research Council Grant (CNCSIS) 109/2007. R E F E R E N C E S [1]. C. Dano, Évaluation de modèles de turbulence pour la simulation d écoulements tridimensionnels instationnaires en turbomachines, Thèse de doctorat, École Centrale de Lyon, 2003 [2]. P. E. Smirnov, T. Hansen and F. R Menter, Numerical Simulation of Turbulent Flows in Centrifugal Compressor Stages with Different Radial Gaps, GT , ASME Turbo Expo 2007: Power for Land, Sea and Air, Montreal, Canada, May 2007

12 150 Mihai Niculescu, Sterian Dănăilă [3]. N. Rochuon, I. Trébinjac and G. Billonnet, An Extraction of the Dominant Rotor-Stator Interaction Modes by the Use of Proper Orthogonal Decomposition (POD), Journal of Thermal Science, Vol. 15, No. 2, June 2006 [4]. N. Rochuon, Analyse de l écoulement tridimensionnel et instationnaire dans un compresseur centrifuge à fort taux de pression, Thèse de doctorat, École Centrale de Lyon, 2007 [5]. S. Dănăilă and C. Berbente, Metode Numerice în Dinamica Fluidelor, (Numerical methods in Fluids Dynamics), Editura Academiei Române, 2003 (in Romanian) [6]. C. Hirsch, Numerical Computation of Internal and External Flow, Volume 2: Computational Methods for Inviscid and Viscous Flows, John Wiley and Sons, New York, 1990 [7]. P. R. Spalart and S. R. Allmaras, A One-Equation Turbulence Model for Aerodynamic Flows, AIAA Paper , 1992 [8]. J. Lumley, Stochastic Tools in Turbulence, Academic Press, 1970 [9]. L. Sirovich, Turbulence and the dynamics of coherent structures, parts I-III. Q. Appl. Math. XLV (3), 1987 [10]. G. Berkooz, P. Holmes and J. Lumley, The Proper Orthogonal Decomposition in the Analysis of Turbulent Flows, Annual Review of Fluid Mechanics, Vol. 25, pp , January 1993 [11]. I. Trébinjac, P. Kulisa, N. Bulot and N. Rochuon, Effect of Unsteadiness on the Performance of a Transonic Centrifugal Compressor Stage, GT , Proceedings of ASME Turbo Expo 2008: Power for Land, Sea and Air, Berlin, Germany, June 2008

Aerodynamic study of a small horizontal-axis wind turbine

Aerodynamic study of a small horizontal-axis wind turbine Aerodynamic study of a small horizontal-axis wind turbine Mihai Leonida NICULESCU*,1, Marius Gabriel COJOCARU 1, Cornelia NITA 1 *Corresponding author *,1 INCAS - National Institute for Aerospace Research

More information

GT UNSTEADY SIMULATION OF A TWO-STAGE COOLED HIGH PRESSURE TURBINE USING AN EFFICIENT NON-LINEAR HARMONIC BALANCE METHOD

GT UNSTEADY SIMULATION OF A TWO-STAGE COOLED HIGH PRESSURE TURBINE USING AN EFFICIENT NON-LINEAR HARMONIC BALANCE METHOD Proceedings of ASME Turbo Expo 213: Turbine Technical Conference and Exposition GT213 June 3-7, 213, San Antonio, Texas, USA GT213-94574 UNSTEADY SIMULATION OF A TWO-STAGE COOLED HIGH PRESSURE TURBINE

More information

Parallel Computations of Unsteady Three-Dimensional Flows in a High Pressure Turbine

Parallel Computations of Unsteady Three-Dimensional Flows in a High Pressure Turbine Parallel Computations of Unsteady Three-Dimensional Flows in a High Pressure Turbine Dongil Chang and Stavros Tavoularis Department of Mechanical Engineering, University of Ottawa, Ottawa, ON Canada Stavros.Tavoularis@uottawa.ca

More information

Mixing-Plane Method for Flutter Computation in Multi-stage Turbomachines

Mixing-Plane Method for Flutter Computation in Multi-stage Turbomachines 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition 5-8 January 2009, Orlando, Florida AIAA 2009-862 Mixing-Plane Method for Flutter Computation in Multi-stage

More information

Applications of Harmonic Balance Method in Periodic Flows Gregor Cvijetić and Inno Gatin

Applications of Harmonic Balance Method in Periodic Flows Gregor Cvijetić and Inno Gatin Applications of Harmonic Balance Method in Periodic Flows Gregor Cvijetić and Inno Gatin Faculty of Mechanical Engineering and Naval Architecture, Zagreb 10000, Croatia, gregor.cvijetic@gmail.com The Harmonic

More information

AA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS

AA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS AA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS 1 / 29 AA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS Hierarchy of Mathematical Models 1 / 29 AA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS 2 / 29

More information

Flow analysis in centrifugal compressor vaneless diffusers

Flow analysis in centrifugal compressor vaneless diffusers 348 Journal of Scientific & Industrial Research J SCI IND RES VOL 67 MAY 2008 Vol. 67, May 2008, pp. 348-354 Flow analysis in centrifugal compressor vaneless diffusers Ozturk Tatar, Adnan Ozturk and Ali

More information

COMPUTATIONAL FLOW ANALYSIS THROUGH A DOUBLE-SUCTION IMPELLER OF A CENTRIFUGAL PUMP

COMPUTATIONAL FLOW ANALYSIS THROUGH A DOUBLE-SUCTION IMPELLER OF A CENTRIFUGAL PUMP Proceedings of the Fortieth National Conference on Fluid Mechanics and Fluid Power December 12-14, 2013, NIT Hamirpur, Himachal Pradesh, India FMFP2013_141 COMPUTATIONAL FLOW ANALYSIS THROUGH A DOUBLE-SUCTION

More information

Contents. 1 Introduction to Gas-Turbine Engines Overview of Turbomachinery Nomenclature...9

Contents. 1 Introduction to Gas-Turbine Engines Overview of Turbomachinery Nomenclature...9 Preface page xv 1 Introduction to Gas-Turbine Engines...1 Definition 1 Advantages of Gas-Turbine Engines 1 Applications of Gas-Turbine Engines 3 The Gas Generator 3 Air Intake and Inlet Flow Passage 3

More information

FLOW CHARACTERISTICS IN A VOLUTE-TYPE CENTRIFUGAL PUMP USING LARGE EDDY SIMULATION

FLOW CHARACTERISTICS IN A VOLUTE-TYPE CENTRIFUGAL PUMP USING LARGE EDDY SIMULATION FLOW CHARACTERISTICS IN A VOLUTE-TYPE CENTRIFUGAL PUMP USING LARGE EDDY SIMULATION Beomjun Kye Keuntae Park Department of Mechanical & Aerospace Engineering Department of Mechanical & Aerospace Engineering

More information

Modeling Unsteady Flow in Turbomachinery Using a Harmonic Balance Technique

Modeling Unsteady Flow in Turbomachinery Using a Harmonic Balance Technique Modeling Unsteady Flow in Turbomachinery Using a Harmonic Balance Technique Torsten Palenschat 317220 30.04.2014 Master seminar CES WS 2013/2014 Center for Computational Engineering Sciences RWTH Aachen

More information

Axial length impact on high-speed centrifugal compressor flow

Axial length impact on high-speed centrifugal compressor flow Fluid Structure Interaction VII 263 Axial length impact on high-speed centrifugal compressor flow P. Le Sausse 1,2,P.Fabrie 1 & D. Arnou 2 1 Université de Bordeaux, IPB, UMR5251, ENSEIRB-MATMECA, Talence,

More information

Numerical and Experimental Investigation of the Flow in a Centrifugal Pump Stage

Numerical and Experimental Investigation of the Flow in a Centrifugal Pump Stage Numerical and Experimental Investigation of the Flow in a Centrifugal Pump Stage FRIEDRICH-KARL BENRA, HANS JOSEF DOHMEN Faculty of Engineering Sciences Department of Mechanical Engineering, Turbomachinery

More information

SIMULATION OF UNSTEADY TURBOMACHINERY FLOWS USING AN IMPLICITLY COUPLED NONLINEAR HARMONIC BALANCE METHOD

SIMULATION OF UNSTEADY TURBOMACHINERY FLOWS USING AN IMPLICITLY COUPLED NONLINEAR HARMONIC BALANCE METHOD Proceedings of ASME Turbo Expo 2011 GT2011 June 6-10, 2011, ancouver, Canada GT2011-46367 SIMULATION OF UNSTEADY TURBOMACHINERY FLOWS USING AN IMPLICITLY COUPLED NONLINEAR HARMONIC BALANCE METHOD Jonathan

More information

Turbulence Modeling. Cuong Nguyen November 05, The incompressible Navier-Stokes equations in conservation form are u i x i

Turbulence Modeling. Cuong Nguyen November 05, The incompressible Navier-Stokes equations in conservation form are u i x i Turbulence Modeling Cuong Nguyen November 05, 2005 1 Incompressible Case 1.1 Reynolds-averaged Navier-Stokes equations The incompressible Navier-Stokes equations in conservation form are u i x i = 0 (1)

More information

Proper Orthogonal Decomposition

Proper Orthogonal Decomposition Proper Orthogonal Decomposition Kameswararao Anupindi School of Mechanical Engineering Purdue University October 15, 2010 Kameswararao Anupindi (Purdue University) ME611, Principles of Turbulence October

More information

Stabilization of Explicit Flow Solvers Using a Proper Orthogonal Decomposition Technique

Stabilization of Explicit Flow Solvers Using a Proper Orthogonal Decomposition Technique 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 09-12 January 2012, Nashville, Tennessee AIAA 2012-1096 Stabilization of Explicit Flow Solvers Using a Proper

More information

The Simulation of Wraparound Fins Aerodynamic Characteristics

The Simulation of Wraparound Fins Aerodynamic Characteristics The Simulation of Wraparound Fins Aerodynamic Characteristics Institute of Launch Dynamics Nanjing University of Science and Technology Nanjing Xiaolingwei 00 P. R. China laithabbass@yahoo.com Abstract:

More information

Multi-frequential harmonic balance approach for the computation of unsteadiness in multi-stage turbomachines

Multi-frequential harmonic balance approach for the computation of unsteadiness in multi-stage turbomachines ème Congrès Français de Mécanique Bordeaux, 6 au août Multi-frequential harmonic balance approach for the computation of unsteadiness in multi-stage turbomachines T Guédeney a, A Gomar a and F Sicot a

More information

The effect of rotational speed variation on the static pressure in the centrifugal pump (part 1)

The effect of rotational speed variation on the static pressure in the centrifugal pump (part 1) IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE) e-issn: 2278-1684,p-ISSN: 2320-334X, Volume 8, Issue 6 (Sep. - Oct. 2013), PP 83-94 The effect of rotational speed variation on the static pressure

More information

WALL ROUGHNESS EFFECTS ON SHOCK BOUNDARY LAYER INTERACTION FLOWS

WALL ROUGHNESS EFFECTS ON SHOCK BOUNDARY LAYER INTERACTION FLOWS ISSN (Online) : 2319-8753 ISSN (Print) : 2347-6710 International Journal of Innovative Research in Science, Engineering and Technology An ISO 3297: 2007 Certified Organization, Volume 2, Special Issue

More information

Performance Investigation of High Pressure Ratio Centrifugal Compressor using CFD

Performance Investigation of High Pressure Ratio Centrifugal Compressor using CFD International Journal of Ignited Minds (IJIMIINDS) Performance Investigation of High Pressure Ratio Centrifugal Compressor using CFD Manjunath DC a, Rajesh b, Dr.V.M.Kulkarni c a PG student, Department

More information

Performance characteristics of turbo blower in a refuse collecting system according to operation conditions

Performance characteristics of turbo blower in a refuse collecting system according to operation conditions Journal of Mechanical Science and Technology 22 (2008) 1896~1901 Journal of Mechanical Science and Technology www.springerlink.com/content/1738-494x DOI 10.1007/s12206-008-0729-6 Performance characteristics

More information

Introduction to Turbomachinery

Introduction to Turbomachinery 1. Coordinate System Introduction to Turbomachinery Since there are stationary and rotating blades in turbomachines, they tend to form a cylindrical form, represented in three directions; 1. Axial 2. Radial

More information

Numerical Prediction Of Torque On Guide Vanes In A Reversible Pump-Turbine

Numerical Prediction Of Torque On Guide Vanes In A Reversible Pump-Turbine Journal of Multidisciplinary Engineering Science and Technology (JMEST) ISSN: 3159 Vol. 2 Issue 6, June - 215 Numerical Prediction Of Torque On Guide Vanes In A Reversible Pump-Turbine Turbine and pump

More information

Helsinki University of Technology Laboratory of Applied Thermodynamics/CFD-Group. MEMO No CFD/TERMO DATE: November 21, 1997

Helsinki University of Technology Laboratory of Applied Thermodynamics/CFD-Group. MEMO No CFD/TERMO DATE: November 21, 1997 Helsinki University of Technology Laboratory of Applied Thermodynamics/CFD-Group MEMO No CFD/TERMO-22-97 DATE: November 21, 1997 TITLE GRV-60 Impeller with airfoil-type and unvaned diffusor AUTHOR(S) Harri

More information

Numerical Analysis of the Flow Through in Centrifugal Pumps

Numerical Analysis of the Flow Through in Centrifugal Pumps Research Article International Journal of Thermal Technologies ISSN 2277-4114 2012 INPRESSCO. All Rights Reserved. Available at http://inpressco.com/category/ijcet Numerical Analysis of the Flow Through

More information

CHAPTER 7 NUMERICAL MODELLING OF A SPIRAL HEAT EXCHANGER USING CFD TECHNIQUE

CHAPTER 7 NUMERICAL MODELLING OF A SPIRAL HEAT EXCHANGER USING CFD TECHNIQUE CHAPTER 7 NUMERICAL MODELLING OF A SPIRAL HEAT EXCHANGER USING CFD TECHNIQUE In this chapter, the governing equations for the proposed numerical model with discretisation methods are presented. Spiral

More information

Numerical Heat and Mass Transfer

Numerical Heat and Mass Transfer Master Degree in Mechanical Engineering Numerical Heat and Mass Transfer 19 Turbulent Flows Fausto Arpino f.arpino@unicas.it Introduction All the flows encountered in the engineering practice become unstable

More information

APPLICATION OF HYBRID CFD/CAA TECHNIQUE FOR MODELING PRESSURE FLUCTUATIONS IN TRANSONIC FLOWS

APPLICATION OF HYBRID CFD/CAA TECHNIQUE FOR MODELING PRESSURE FLUCTUATIONS IN TRANSONIC FLOWS TASK QUARTERLY Vol. 17, Nos 3 4, 2013, pp. 145 154 APPLICATION OF HYBRID CFD/CAA TECHNIQUE FOR MODELING PRESSURE FLUCTUATIONS IN TRANSONIC FLOWS SŁAWOMIR DYKAS, WŁODZIMIERZ WRÓBLEWSKI AND SEBASTIAN RULIK

More information

A Computational Investigation of a Turbulent Flow Over a Backward Facing Step with OpenFOAM

A Computational Investigation of a Turbulent Flow Over a Backward Facing Step with OpenFOAM 206 9th International Conference on Developments in esystems Engineering A Computational Investigation of a Turbulent Flow Over a Backward Facing Step with OpenFOAM Hayder Al-Jelawy, Stefan Kaczmarczyk

More information

Numerical investigation of the flow instabilities in centrifugal fan

Numerical investigation of the flow instabilities in centrifugal fan Proceedings of the 4th WSEAS International Conference on Fluid Mechanics and Aerodynamics, Elounda, Greece, August 21-23, 26 (pp282-288) Numerical investigation of the flow instabilities in centrifugal

More information

Parallel Computation of Turbine Blade Clocking

Parallel Computation of Turbine Blade Clocking Parallel Computation of Turbine Blade Clocking Paul G. A. Cizmas Department of Aerospace Engineering Texas A&M University College Station, Texas 77843-34 Daniel J. Dorney Department of Mechanical Engineering

More information

39th AIAA Aerospace Sciences Meeting and Exhibit January 8 11, 2001/Reno, NV

39th AIAA Aerospace Sciences Meeting and Exhibit January 8 11, 2001/Reno, NV AIAA 2 529 Unsteady Flow Investigations in an Axial Turbine Using the Massively Parallel Flow Solver TFLO Jixian Yao, Roger L. Davis, Juan J. Alonso, and Antony Jameson Stanford University, Stanford, CA

More information

LARGE EDDY SIMULATION OF FLOW OVER NOZZLE GUIDE VANE OF A TRANSONIC HIGH PRESSURE TURBINE

LARGE EDDY SIMULATION OF FLOW OVER NOZZLE GUIDE VANE OF A TRANSONIC HIGH PRESSURE TURBINE 20 th Annual CFD Symposium, August 09-10, 2018, Bangalore LARGE EDDY SIMULATION OF FLOW OVER NOZZLE GUIDE VANE OF A TRANSONIC HIGH PRESSURE TURBINE Bharathan R D, Manigandan P, Vishal Tandon, Sharad Kapil,

More information

Effect of modification to tongue and basic circle diameter on vibration in a double-suction centrifugal pump

Effect of modification to tongue and basic circle diameter on vibration in a double-suction centrifugal pump 5th International Conference on Information Engineering for Mechanics and Materials (ICIMM 2015) Effect of modification to tongue and basic circle diameter on vibration in a double-suction centrifugal

More information

Steady state operation simulation of the Francis- 99 turbine by means of advanced turbulence models

Steady state operation simulation of the Francis- 99 turbine by means of advanced turbulence models Journal of Physics: Conference Series PAPER OPEN ACCESS Steady state operation simulation of the Francis- 99 turbine by means of advanced turbulence models To cite this article: A Gavrilov et al 2017 J.

More information

Radial Compressors. Damian Vogt Course MJ2429. Nomenclature

Radial Compressors. Damian Vogt Course MJ2429. Nomenclature Turbomachinery Lecture Notes 1 007-10-04 Radial Compressors Damian Vogt Course MJ49 Nomenclature Subscripts Symbol Denotation Unit c Absolute velocity m/s h Enthalpy J/kg m& Mass flow rate kg/s r Radius

More information

GPPS NUMERICAL PREDICTION OF UNSTEADY ENDWALL FLOW AND HEAT TRANSFER WITH ONCOMING WAKE

GPPS NUMERICAL PREDICTION OF UNSTEADY ENDWALL FLOW AND HEAT TRANSFER WITH ONCOMING WAKE Proceedings of Shanghai 17 Global Power and Propulsion Forum 3 th October 1 st November, 17 http://www.gpps.global GPPS-17-133 NUMERICAL PREDICTION OF UNSTEADY ENDWALL FLOW AND HEAT TRANSFER WITH ONCOMING

More information

Manhar Dhanak Florida Atlantic University Graduate Student: Zaqie Reza

Manhar Dhanak Florida Atlantic University Graduate Student: Zaqie Reza REPRESENTING PRESENCE OF SUBSURFACE CURRENT TURBINES IN OCEAN MODELS Manhar Dhanak Florida Atlantic University Graduate Student: Zaqie Reza 1 Momentum Equations 2 Effect of inclusion of Coriolis force

More information

Active Control of Separated Cascade Flow

Active Control of Separated Cascade Flow Chapter 5 Active Control of Separated Cascade Flow In this chapter, the possibility of active control using a synthetic jet applied to an unconventional axial stator-rotor arrangement is investigated.

More information

TURBINE FORCED RESPONSE PREDICTION USING AN INTEGRATED NONLINEAR ANALYSIS A.I. Sayma, M. Vahdati & M. Imregun Abstract The forced response due to flow

TURBINE FORCED RESPONSE PREDICTION USING AN INTEGRATED NONLINEAR ANALYSIS A.I. Sayma, M. Vahdati & M. Imregun Abstract The forced response due to flow TURBINE FORCED RESPONSE PREDICTION USING AN INTEGRATED NONLINEAR ANALYSIS A.I. Sayma, M. Vahdati & M. Imregun 1 Imperial College of Science Technology and Medicine Mechanical Engineering Department Exhibition

More information

Differential relations for fluid flow

Differential relations for fluid flow Differential relations for fluid flow In this approach, we apply basic conservation laws to an infinitesimally small control volume. The differential approach provides point by point details of a flow

More information

In this lecture... Centrifugal compressors Thermodynamics of centrifugal compressors Components of a centrifugal compressor

In this lecture... Centrifugal compressors Thermodynamics of centrifugal compressors Components of a centrifugal compressor Lect- 3 In this lecture... Centrifugal compressors Thermodynamics of centrifugal compressors Components of a centrifugal compressor Centrifugal compressors Centrifugal compressors were used in the first

More information

Improved Model for Meanline Analysis of Centrifugal Compressors with a Large Tip Clearance

Improved Model for Meanline Analysis of Centrifugal Compressors with a Large Tip Clearance Improved Model for Meanline Analysis of Centrifugal Compressors with a Large Tip Clearance Andrey Sherbina 1, Ivan Klimov 2 and Leonid Moroz 3 SoftInWay Inc., 1500 District Avenue, Burlington, MA, 01803,

More information

2. Conservation Equations for Turbulent Flows

2. Conservation Equations for Turbulent Flows 2. Conservation Equations for Turbulent Flows Coverage of this section: Review of Tensor Notation Review of Navier-Stokes Equations for Incompressible and Compressible Flows Reynolds & Favre Averaging

More information

CDF CALCULATION OF RADIAL FAN STAGE WITH VARIABLE LENGTH OF SEMI BLADES SVOČ FST 2012

CDF CALCULATION OF RADIAL FAN STAGE WITH VARIABLE LENGTH OF SEMI BLADES SVOČ FST 2012 CDF CALCULATION OF RADIAL FAN STAGE WITH VARIABLE LENGTH OF SEMI BLADES SVOČ FST 2012 Ing. Roman Gášpár, Západočeská univerzita v Plzni, Univerzitní 8, 306 14 Plzeň Česká republika NOMENCLATURE A area

More information

Study of the Losses in Fluid Machinery with the Help of Entropy

Study of the Losses in Fluid Machinery with the Help of Entropy Study of the Losses in Fluid Machinery with the Help of Entropy Martin Böhle 1, Annika Fleder 1, Matthias Mohr 1 * SYMPOSIA ON ROTATING MACHINERY ISROMAC 16 International Symposium on Transport Phenomena

More information

CFD Investigation of Flow Structures in Rotor-Stator Disc Cavity Systems. Minoo Arzpeima

CFD Investigation of Flow Structures in Rotor-Stator Disc Cavity Systems. Minoo Arzpeima CFD Investigation of Flow Structures in Rotor-Stator Disc Cavity Systems Minoo Arzpeima i Master of Science Thesis EGI 2014 CFD Investigation of Flow Structures in Rotor-Stator Disc Cavity Systems Minoo

More information

EFFECT OF FORCED ROTATING VANELESS DIFFUSERS ON CENTRIFUGAL COMPRESSOR STAGE PERFORMANCE

EFFECT OF FORCED ROTATING VANELESS DIFFUSERS ON CENTRIFUGAL COMPRESSOR STAGE PERFORMANCE Journal of Engineering Science and Technology Vol. 6, No. 5 (2011) 558-574 School of Engineering, Taylor s University EFFECT OF FORCED ROTATING VANELESS DIFFUSERS ON CENTRIFUGAL COMPRESSOR STAGE PERFORMANCE

More information

Numerical Simulation of a Complete Francis Turbine including unsteady rotor/stator interactions

Numerical Simulation of a Complete Francis Turbine including unsteady rotor/stator interactions Numerical Simulation of a Complete Francis Turbine including unsteady rotor/stator interactions Ruprecht, A., Heitele, M., Helmrich, T. Institute for Fluid Mechanics and Hydraulic Machinery University

More information

Reynolds number effects on the aerodynamics of compact axial compressors

Reynolds number effects on the aerodynamics of compact axial compressors Paper ID: ETC27-227 Proceedings of 2th European Conference on Turbomachinery Fluid dynamics & Thermodynamics ETC2, April 3-7, 27; Stockholm, Sweden Reynolds number effects on the aerodynamics of compact

More information

THERMAL ANALYSIS OF SECOND STAGE GAS TURBINE ROTOR BLADE

THERMAL ANALYSIS OF SECOND STAGE GAS TURBINE ROTOR BLADE Polymers Research Journal ISSN: 195-50 Volume 6, Number 01 Nova Science Publishers, Inc. THERMAL ANALYSIS OF SECOND STAGE GAS TURBINE ROTOR BLADE E. Poursaeidi, M. Mohammadi and S. S. Khamesi University

More information

Circular Bearing Performance Parameters with Isothermal and Thermo-Hydrodynamic Approach Using Computational Fluid Dynamics

Circular Bearing Performance Parameters with Isothermal and Thermo-Hydrodynamic Approach Using Computational Fluid Dynamics Circular Bearing Performance Parameters with Isothermal and Thermo-Hydrodynamic Approach Using Computational Fluid Dynamics Amit Chauhan 1 Department of Mechanical Engineering, University Institute of

More information

FLOW PATTERN STUDY OF A CENTRIFUGAL PUMP USING CFD METHODS CONCENTRATING ON VOLUTE TONGUE ROLE

FLOW PATTERN STUDY OF A CENTRIFUGAL PUMP USING CFD METHODS CONCENTRATING ON VOLUTE TONGUE ROLE FLOW PATTERN STUDY OF A CENTRIFUGAL PUMP USING CFD METHODS CONCENTRATING ON VOLUTE TONGUE ROLE N. Pourmahmoud and S. Majid Taleby Faculty of Engineering, Urmia University, Urmia, Iran E-Mail: majid.taleby@gmail.com

More information

THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS Three Perk Avenue, New YoriL N.Y Institute of Turbomachinery

THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS Three Perk Avenue, New YoriL N.Y Institute of Turbomachinery THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS Three Perk Avenue, New YoriL N.Y. 100164990 99-GT-103 The Society shall not be responsible for statements or opinions advanced in papers or discussion at meetings

More information

Zonal modelling approach in aerodynamic simulation

Zonal modelling approach in aerodynamic simulation Zonal modelling approach in aerodynamic simulation and Carlos Castro Barcelona Supercomputing Center Technical University of Madrid Outline 1 2 State of the art Proposed strategy 3 Consistency Stability

More information

Aero-Acoustic assessment of installed propellers

Aero-Acoustic assessment of installed propellers Aero-Acoustic assessment of installed propellers Marius Gabriel COJOCARU*,1, Mihai Leonida NICULESCU 1, Mihai Victor PRICOP 1 *Corresponding author *,1 INCAS National Institute for Aerospace Research Elie

More information

Direct Numerical Simulations of a Two-dimensional Viscous Flow in a Shocktube using a Kinetic Energy Preserving Scheme

Direct Numerical Simulations of a Two-dimensional Viscous Flow in a Shocktube using a Kinetic Energy Preserving Scheme 19th AIAA Computational Fluid Dynamics - 5 June 009, San Antonio, Texas AIAA 009-3797 19th AIAA Computational Fluid Dynamics Conference, - 5 June 009, San Antonio, Texas Direct Numerical Simulations of

More information

A Numerical study of effect of Return Channel Vanes Shroud Wall Divergence Angle on the Cross-over System Performance in Centrifugal Compressors

A Numerical study of effect of Return Channel Vanes Shroud Wall Divergence Angle on the Cross-over System Performance in Centrifugal Compressors RESEARCH ARTICLE OPEN ACCESS A Numerical study of effect of Return Channel Vanes Shroud Wall Divergence Angle on the Cross-over System Performance in Centrifugal Compressors * K.Srinivasa Reddy *, M Sai

More information

Aerodynamic force analysis in high Reynolds number flows by Lamb vector integration

Aerodynamic force analysis in high Reynolds number flows by Lamb vector integration Aerodynamic force analysis in high Reynolds number flows by Lamb vector integration Claudio Marongiu, Renato Tognaccini 2 CIRA, Italian Center for Aerospace Research, Capua (CE), Italy E-mail: c.marongiu@cira.it

More information

Turbulent Boundary Layers & Turbulence Models. Lecture 09

Turbulent Boundary Layers & Turbulence Models. Lecture 09 Turbulent Boundary Layers & Turbulence Models Lecture 09 The turbulent boundary layer In turbulent flow, the boundary layer is defined as the thin region on the surface of a body in which viscous effects

More information

PARAMETRIC STUDY PERFORMANCE OF A CENTRIFUGAL PUMP BASED ON SIMPLE AND DOUBLE-ARC BLADE DESIGN METHODS

PARAMETRIC STUDY PERFORMANCE OF A CENTRIFUGAL PUMP BASED ON SIMPLE AND DOUBLE-ARC BLADE DESIGN METHODS 3 rd International Conference on Experiments/Process/System Modeling/Simulation & Optimization 3 rd IC-EpsMsO Athens, 8- July, 2009 IC-EpsMsO PARAMETRIC STUDY PERFORMANCE OF A CENTRIFUGAL PUMP BASED ON

More information

Numerical Modelling of Aerodynamic Noise in Compressible Flows

Numerical Modelling of Aerodynamic Noise in Compressible Flows Open Journal of Fluid Dynamics 22 2 65-69 http://dx.doi.org/.4236/ofd.22.237 Published Online September 22 (http://www.scirp.org/ournal/ofd) Numerical Modelling of Aerodynamic Noise in Compressible Flows

More information

GT NUMERICAL COMPUTATION OF THE JET IMPINGEMENT COOLING OF HIGH PRESSURE RATIO COMPRESSORS

GT NUMERICAL COMPUTATION OF THE JET IMPINGEMENT COOLING OF HIGH PRESSURE RATIO COMPRESSORS Proceedings of ASME Turbo Expo 2013 GT2013 June 3-7, 2013, San Antonio, Texas, USA GT2013-94949 NUMERICAL COMPUTATION OF THE JET IMPINGEMENT COOLING OF HIGH PRESSURE RATIO COMPRESSORS Elmar Gröschel ABB

More information

Loss Mechanism and Assessment in Mixing Between Main Flow and Coolant Jets with DDES Simulation

Loss Mechanism and Assessment in Mixing Between Main Flow and Coolant Jets with DDES Simulation Proceedings of Shanghai 2017 Global Power and Propulsion Forum 30 th October 1 st November, 2017 http://www.gpps.global 0200 Loss Mechanism and Assessment in Mixing Between Main Flow and Coolant Jets with

More information

Numerical Analysis of Partial Admission in Axial Turbines. Narmin Baagherzadeh Hushmandi

Numerical Analysis of Partial Admission in Axial Turbines. Narmin Baagherzadeh Hushmandi Numerical Analysis of Partial Admission in Axial Turbines Narmin Baagherzadeh Hushmandi Doctoral Thesis 2010 II Doctoral Thesis Report / Narmin B. Hushmandi 2009 ABSTRACT Numerical analysis of partial

More information

Comparison of Turbulence Models in the Flow over a Backward-Facing Step Priscila Pires Araujo 1, André Luiz Tenório Rezende 2

Comparison of Turbulence Models in the Flow over a Backward-Facing Step Priscila Pires Araujo 1, André Luiz Tenório Rezende 2 Comparison of Turbulence Models in the Flow over a Backward-Facing Step Priscila Pires Araujo 1, André Luiz Tenório Rezende 2 Department of Mechanical and Materials Engineering, Military Engineering Institute,

More information

Numerical Simulation of Rocket Engine Internal Flows

Numerical Simulation of Rocket Engine Internal Flows Numerical Simulation of Rocket Engine Internal Flows Project Representative Masao Furukawa Authors Taro Shimizu Nobuhiro Yamanishi Chisachi Kato Nobuhide Kasagi Institute of Space Technology and Aeronautics,

More information

NUMERICAL ANALYSIS OF TURBULENT FLOW IN CENTRIFUGAL PUMP

NUMERICAL ANALYSIS OF TURBULENT FLOW IN CENTRIFUGAL PUMP 224 Military Technical College Kobry El-Kobbah, Cairo, Egypt. 17 th International Conference on Applied Mechanics and Mechanical Engineering. NUMERICAL ANALYSIS OF TURBULENT FLOW IN CENTRIFUGAL PU S. M.

More information

Two-Dimensional Rotating Stall Analysis in a Wide Vaneless Diffuser

Two-Dimensional Rotating Stall Analysis in a Wide Vaneless Diffuser Hindawi Publishing Corporation International Journal of Rotating Machinery Volume 6, Article ID 564, Pages 1 11 DOI 1.1155/IJRM/6/564 Two-Dimensional Rotating Stall Analysis in a Wide Vaneless Diffuser

More information

OPTIMAL DESIGN OF CLUTCH PLATE BASED ON HEAT AND STRUCTURAL PARAMETERS USING CFD AND FEA

OPTIMAL DESIGN OF CLUTCH PLATE BASED ON HEAT AND STRUCTURAL PARAMETERS USING CFD AND FEA International Journal of Mechanical Engineering and Technology (IJMET) Volume 9, Issue 5, May 2018, pp. 717 724, Article ID: IJMET_09_05_079 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=9&itype=5

More information

Application of Computational Fluid Dynamics to Practical Design and Performance Analysis of Turbomachinery

Application of Computational Fluid Dynamics to Practical Design and Performance Analysis of Turbomachinery 10 Application of Computational Fluid Dynamics to Practical Design and Performance Analysis of Turbomachinery Hyoung Woo OH Chungju National University Korea 1. Introduction Over the past several decades,

More information

ENGINEERING MECHANICS 2012 pp Svratka, Czech Republic, May 14 17, 2012 Paper #195

ENGINEERING MECHANICS 2012 pp Svratka, Czech Republic, May 14 17, 2012 Paper #195 . 18 m 2012 th International Conference ENGINEERING MECHANICS 2012 pp. 309 315 Svratka, Czech Republic, May 14 17, 2012 Paper #195 NUMERICAL SIMULATION OF TRANSITIONAL FLOWS WITH LAMINAR KINETIC ENERGY

More information

Chapter 5. The Differential Forms of the Fundamental Laws

Chapter 5. The Differential Forms of the Fundamental Laws Chapter 5 The Differential Forms of the Fundamental Laws 1 5.1 Introduction Two primary methods in deriving the differential forms of fundamental laws: Gauss s Theorem: Allows area integrals of the equations

More information

Analysis of Heat Transfer in Pipe with Twisted Tape Inserts

Analysis of Heat Transfer in Pipe with Twisted Tape Inserts Proceedings of the 2 nd International Conference on Fluid Flow, Heat and Mass Transfer Ottawa, Ontario, Canada, April 30 May 1, 2015 Paper No. 143 Analysis of Heat Transfer in Pipe with Twisted Tape Inserts

More information

Numerical Methods in Aerodynamics. Turbulence Modeling. Lecture 5: Turbulence modeling

Numerical Methods in Aerodynamics. Turbulence Modeling. Lecture 5: Turbulence modeling Turbulence Modeling Niels N. Sørensen Professor MSO, Ph.D. Department of Civil Engineering, Alborg University & Wind Energy Department, Risø National Laboratory Technical University of Denmark 1 Outline

More information

ENERGY TRANSFER BETWEEN FLUID AND ROTOR. Dr. Ir. Harinaldi, M.Eng Mechanical Engineering Department Faculty of Engineering University of Indonesia

ENERGY TRANSFER BETWEEN FLUID AND ROTOR. Dr. Ir. Harinaldi, M.Eng Mechanical Engineering Department Faculty of Engineering University of Indonesia ENERGY TRANSFER BETWEEN FLUID AND ROTOR Dr. Ir. Harinaldi, M.Eng Mechanical Engineering Department Faculty of Engineering University of Indonesia Basic Laws and Equations Continuity Equation m m ρ mass

More information

GTINDIA CFD ANALYSIS TO UNDERSTAND THE FLOW BEHAVIOUR OF A SINGLE STAGE TRANSONIC AXIAL FLOW COMPRESSOR. 1 Copyright 2013 by ASME

GTINDIA CFD ANALYSIS TO UNDERSTAND THE FLOW BEHAVIOUR OF A SINGLE STAGE TRANSONIC AXIAL FLOW COMPRESSOR. 1 Copyright 2013 by ASME Proceedings of ASME GTINDIA 203 ASME 203 GAS TURBINE INDIA CONFERENCE DECEMBER 5-6, 203, BANGALORE, KARNATAKA, INDIA GTINDIA203-3592 CFD ANALYSIS TO UNDERSTAND THE FLOW BEHAVIOUR OF A SINGLE STAGE TRANSONIC

More information

Turbine Blade Cascade Heat Transfer Analysis Using CFD A Review

Turbine Blade Cascade Heat Transfer Analysis Using CFD A Review IJSE International Journal of Science echnology & Engineering Vol. 1, Issue 7, January 015 ISSN(online): 349-784X urbine Blade Cascade Heat ransfer Analysis Using CFD A Review MD.Hasheer.Sk Assistant Professor

More information

Turbomachinery Applications with the Time Spectral Method

Turbomachinery Applications with the Time Spectral Method 35th AIAA Fluid Dynamics Conference and Exhibit, June 6-9,005, Toronto,Ontario Turbomachinery Applications with the Time Spectral Method Edwin van der Weide, Arathi K Gopinath and Antony Jameson Stanford

More information

Non-Synchronous Vibrations of Turbomachinery Airfoils

Non-Synchronous Vibrations of Turbomachinery Airfoils Non-Synchronous Vibrations of Turbomachinery Airfoils 600 500 NSV Frequency,!, hz 400 300 200 F.R. Flutter 100 SFV 0 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 Rotor Speed,!, RPM Kenneth C. Hall,

More information

Tutorial School on Fluid Dynamics: Aspects of Turbulence Session I: Refresher Material Instructor: James Wallace

Tutorial School on Fluid Dynamics: Aspects of Turbulence Session I: Refresher Material Instructor: James Wallace Tutorial School on Fluid Dynamics: Aspects of Turbulence Session I: Refresher Material Instructor: James Wallace Adapted from Publisher: John S. Wiley & Sons 2002 Center for Scientific Computation and

More information

Numerical Researches on Aeroelastic Problem of a Rotor due to IGV/Fan Interaction

Numerical Researches on Aeroelastic Problem of a Rotor due to IGV/Fan Interaction 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition 5-8 January 9, Orlando, Florida AIAA 9-865 Numerical Researches on Aeroelastic Problem of a Rotor due to IGV/Fan

More information

STUDY ON TIP LEAKAGE VORTEX IN AN AXIAL FLOW PUMP BASED ON MODIFIED SHEAR STRESS TRANSPORT k-ω TURBULENCE MODEL

STUDY ON TIP LEAKAGE VORTEX IN AN AXIAL FLOW PUMP BASED ON MODIFIED SHEAR STRESS TRANSPORT k-ω TURBULENCE MODEL THERMAL SCIENCE, Year 213, Vol. 17, No. 5, pp. 1551-1555 1551 STUDY ON TIP AKAGE VORX IN AN AXIAL FLOW PUMP BASED ON MODIFIED SHEAR STRE TRANSPORT k-ω TURBUNCE MODEL Introduction by Desheng ZHANG *, Dazhi

More information

Computation of hypersonic shock boundary layer interaction on a double wedge using a differential Reynolds Stress Model

Computation of hypersonic shock boundary layer interaction on a double wedge using a differential Reynolds Stress Model Computation of hypersonic shock boundary layer interaction on a double wedge using a differential Reynolds Stress Model A. Bosco AICES, Templergraben 55, Aachen, 52056, Germany B. Reinartz CATS, Theaterplatz

More information

Effect of Shape and Flow Control Devices on the Fluid Flow Characteristics in Three Different Industrial Six Strand Billet Caster Tundish

Effect of Shape and Flow Control Devices on the Fluid Flow Characteristics in Three Different Industrial Six Strand Billet Caster Tundish , pp. 1647 1656 Effect of Shape and Flow Control Devices on the Fluid Flow Characteristics in Three Different Industrial Six Strand Billet Caster Tundish Anurag TRIPATHI and Satish Kumar AJMANI Research

More information

Lecture Notes Fluid Mechanics of Turbomachines II

Lecture Notes Fluid Mechanics of Turbomachines II Lecture Notes Fluid Mechanics of Turbomachines II N.P. Kruyt 999-2009 N.P. Kruyt Turbomachinery Laboratory Engineering Fluid Dynamics Department of Mechanical Engineering University of Twente The Netherlands

More information

(U c. t)/b (U t)/b

(U c. t)/b (U t)/b DYNAMICAL MODELING OF THE LARGE-SCALE MOTION OF A PLANAR TURBULENT JET USING POD MODES. S. Gordeyev 1 and F. O. Thomas 1 University of Notre Dame, Notre Dame, USA University of Notre Dame, Notre Dame,

More information

NUMERICAL INVESTIGATION OF A TWO-STAGE COUNTER-ROTATING TURBINE WITH TRANSITION MODELING AND PREDICTION IMPROVEMENT WITH TIME-ACCURATE CALCULATIONS

NUMERICAL INVESTIGATION OF A TWO-STAGE COUNTER-ROTATING TURBINE WITH TRANSITION MODELING AND PREDICTION IMPROVEMENT WITH TIME-ACCURATE CALCULATIONS NUMERICAL INVESTIGATION OF A TWO-STAGE COUNTER-ROTATING TURBINE WITH TRANSITION MODELING AND PREDICTION IMPROVEMENT WITH TIME-ACCURATE CALCULATIONS M. Bugra Akin, Wolfgang Sanz Institute for Thermal Turbomachinery

More information

PERFORMANCE SCREENING OF A LOUVERED FIN AND VORTEX GENERATOR COMBINATION

PERFORMANCE SCREENING OF A LOUVERED FIN AND VORTEX GENERATOR COMBINATION HEFAT2014 10 th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics 14 26 July 2014 Orlando, Florida PERFORMANCE SCREENING OF A LOUVERED FIN AND VORTEX GENERATOR COMBINATION Bernd

More information

CFD Analysis for Thermal Behavior of Turbulent Channel Flow of Different Geometry of Bottom Plate

CFD Analysis for Thermal Behavior of Turbulent Channel Flow of Different Geometry of Bottom Plate International Journal Of Engineering Research And Development e-issn: 2278-067X, p-issn: 2278-800X, www.ijerd.com Volume 13, Issue 9 (September 2017), PP.12-19 CFD Analysis for Thermal Behavior of Turbulent

More information

Numerical Investigation of Fluid Flows over a Rotor-Stator(Stage) in an Axial Flow Compressor Stage

Numerical Investigation of Fluid Flows over a Rotor-Stator(Stage) in an Axial Flow Compressor Stage Numerical Investigation of Fluid Flows over a Rotor-Stator(Stage) in an Axial Flow Compressor Stage Mr Vamsi Krishna Chowduru, Mr A Sai Kumar, Dr Madhu, Mr T Mahendar M.Tech (Thermal Engineering), MLR

More information

Effects of the Leakage Flow Tangential Velocity in Shrouded Axial Compressor Cascades *

Effects of the Leakage Flow Tangential Velocity in Shrouded Axial Compressor Cascades * TSINGHUA SCIENCE AND TECHNOLOGY ISSNll1007-0214ll21/21llpp105-110 Volume 14, Number S2, December 2009 Effects of the Leakage Flow Tangential Velocity in Shrouded Axial Compressor Cascades * KIM Jinwook

More information

A PARAMETRIC DESIGN OF COMPACT EXHAUST MANIFOLD JUNCTION IN HEAVY DUTY DIESEL ENGINE USING COMPUTATIONAL FLUID DYNAMICS CODES

A PARAMETRIC DESIGN OF COMPACT EXHAUST MANIFOLD JUNCTION IN HEAVY DUTY DIESEL ENGINE USING COMPUTATIONAL FLUID DYNAMICS CODES THERMAL SCIENCE, Year 011, Vol. 15, No. 4, pp. 103-1033 103 A PARAMETRIC DESIGN OF COMPACT EXHAUST MANIFOLD JUNCTION IN HEAVY DUTY DIESEL ENGINE USING COMPUTATIONAL FLUID DYNAMICS CODES by Hessamedin NAEIMI

More information

CHAPTER 7 SEVERAL FORMS OF THE EQUATIONS OF MOTION

CHAPTER 7 SEVERAL FORMS OF THE EQUATIONS OF MOTION CHAPTER 7 SEVERAL FORMS OF THE EQUATIONS OF MOTION 7.1 THE NAVIER-STOKES EQUATIONS Under the assumption of a Newtonian stress-rate-of-strain constitutive equation and a linear, thermally conductive medium,

More information

Simulation of Vortex Shedding in a Turbine Stage

Simulation of Vortex Shedding in a Turbine Stage THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS 345 E. 47th St_, New York, N.Y. 10017 ^s-gt-242 SThe Society shall not be responsible for statements or opinions advanced in papers or discussion at meetings

More information

Parametric Investigation of Hull Shaped Fuselage for an Amphibious UAV

Parametric Investigation of Hull Shaped Fuselage for an Amphibious UAV Ninth International Conference on Computational Fluid Dynamics (ICCFD9), Istanbul, Turkey, July 11-15, 2016 ICCFD9-2016-226 Parametric Investigation of Hull Shaped Fuselage for an Amphibious UAV Emre Sazak

More information

CFD with OpenSource software

CFD with OpenSource software CFD with OpenSource software The Harmonic Balance Method in foam-extend Gregor Cvijetić Supervisor: Hrvoje Jasak Faculty of Mechanical Engineering and Naval Architecture University of Zagreb gregor.cvijetic@fsb.hr

More information